U.S. patent number 3,910,375 [Application Number 05/499,333] was granted by the patent office on 1975-10-07 for jet engine silencer.
This patent grant is currently assigned to Bertin & Cie. Invention is credited to Jean-Pierre Achille Allioud, Claude Charles Doyotte, Jean Georges Edouard Joseph Hache.
United States Patent |
3,910,375 |
Hache , et al. |
October 7, 1975 |
Jet engine silencer
Abstract
In and for a jet propulsion engine having a thrust nozzle
adapted to exhaust a propulsive gas jet, said nozzle including wall
means longitudinally bounding a hollow central body substantially
coaxial with said nozzle, a silencer device for reducing the noise
produced by said gas jet, said silencer device comprising means for
supplying the inside of said hollow central body with air, and at
least one orifice formed in said wall means and through which air
from the inside of said hollow central body can discharge into the
gas jet exhausting from said thrust nozzle, wherein the improvement
comprises, hingedly connected to the central body, at least one
adjustable obturating flap movable between a first position wherein
it unmasks said orifice and a second position wherein it masks the
same and restores a substantially unbroken surface to the
longitudinal wall of the central body.
Inventors: |
Hache; Jean Georges Edouard
Joseph (Fontenay-le-Fleury, FR), Allioud; Jean-Pierre
Achille (Velisy, FR), Doyotte; Claude Charles (Le
Plessis Robinson, FR) |
Assignee: |
Bertin & Cie (Plaisir,
FR)
|
Family
ID: |
9124147 |
Appl.
No.: |
05/499,333 |
Filed: |
August 19, 1974 |
Foreign Application Priority Data
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Aug 21, 1973 [FR] |
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73.30277 |
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Current U.S.
Class: |
181/215; 60/262;
181/220; 239/265.17; 60/226.1; 60/264; 239/265.13 |
Current CPC
Class: |
F02K
1/383 (20130101) |
Current International
Class: |
F02K
1/38 (20060101); F02K 1/00 (20060101); B64d
033/06 () |
Field of
Search: |
;181/33HB,33HC,33HD,43,51 ;60/226,262,264 ;239/265.13,265.17 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Hartary; Joseph W.
Assistant Examiner: Gonzales; John F.
Attorney, Agent or Firm: Breiner; A. W.
Claims
What we claim is:
1. In and for a jet propulsion engine having a thrust nozzle
adapted to exhaust a propulsive gas jet, said nozzle including wall
means longitudinally bounding a hollow central body substantially
coaxial with said nozzle, a silencer device for reducing the noise
produced by said gas jet, said silencer device comprising means for
supplying the inside of said hollow central body with air, and at
least one orifice formed in said wall means and through which air
from the inside of said hollow central body can discharge into the
gas jet exhausting from said thrust nozzle, wherein the improvement
comprises, hingedly connected to the central body, at least one
adjustable obturating flap movable between a first position wherein
it unmasks said orifice and a second position wherein it masks the
same and restores a substantially unbroken surface to the
longitudinal wall of the central body.
2. A silencer device according to claim 1, wherein the flap
comprises a hollow body having an open upstream end which always
lies inside said central body, and a likewise open downstream end
which when said orifice is masked lies inside the central body and
when said orifice is unmasked projects into the gas jet.
3. A silencer device according to claim 1, further comprising an
adjustable deflecting member in the shape of a dihedron projecting
into the gas jet with its edge extending substantially transversely
to the nozzle axis when said orifice is unmasked.
4. A silencer device according to claim 1, wherein the flap is
hingedly connected to the central body about a hinge line having a
component substantially parallel to the nozzle axis.
5. A silencer device according to claim 1, wherein the nozzle
comprises a discharge edge situated upstream of the said
orifice.
6. A silencer device according to claim 5, further comprising an
auxiliary fairing coaxial with the nozzle, said fairing being
disposed at least partly downstream of the said discharge edge and
having an upstream diameter greater than the largest dimension of
the downstream portion of a cowling containing the jet engine.
7. A silencer device according to claim 6, further comprising means
for moving said auxiliary fairing in a direction parallel to the
nozzle axis, between an extended postion in which the auxiliary
fairing functions as an exhaust diffuser around the said gas jet
and a retracted position in which it surrounds the said engine
cowling.
8. A silencer device according to claim 1, wherein the means for
supplying the inside of the hollow central body with air comprise
an ejector fed with a pressurized inducing fluid.
9. A silencer device according to claim 1, in and for a jet
propulsion engine having an multistage compressor, wherein the
means for supplying the inside of the hollow central body with air
include at least one passageway originating between two stages of
said compressor.
10. A silencer device according to claim 1, in and for a jet
propulsion engine of the dual-flow type, namely a heated gas flow
and an unheated air flow, wherein the means for supplying the
inside of the hollow central body with air comprise means for
drawing air from said unheated air flow.
Description
The present invention relates to a silencer device for reducing the
noise produced by a propulsive gas jet exhausting from the thrust
nozzle of a jet propulsion engine, said nozzle including wall means
longitudinally bounding a hollow central body substantially coaxial
with said nozzle, said silencer device being of the kind comprising
means for supplying the inside of said hollow central body with
air, and at least one orifice formed in said wall means and through
which air from the inside of said hollow central body can discharge
into the said gas jet.
The invention has for its object, firstly, to improve the noise
abatement effect resulting from placing the gas jet in contact with
air issuing from the hollow central body and, secondly, to allow of
cancelling this noise abatement effect when it is no longer
required.
In accordance with the invention, there is provided, hingedly
connected to the central body, at least one adjustable obturating
flap movable between a first or operative position wherein it
unmasks the aforesaid orifice, and a second or inoperative position
wherein it masks the same and restores a substantially unbroken
surface to the longitudinal wall of the central body.
In accordance with an embodiment of the invention, the flap
comprises a hollow body having an open upstream end which always
lies inside said central body, and a likewise open downstream end
which when said orifice is masked lies inside the central body and
when said orifice is unmasked projects into the gas jet.
In accordance with another embodiment of the invention, the
silencer further includes a generally dihedronshaped deflector
member supported by the central body and capable of occupying
either an operative or deployed position wherein it projects into
the gas jet and its edge extends substantially transversely to the
nozzle axis, the interior of said dihedron then facing downstream,
or an inoperative position wherein it is retracted into said
central body.
The description which follows with reference to the accompanying
non-limitative exemplary drawing will give a clear understanding of
how the invention can be carried into practice.
In the drawing:
FIG. 1 is a diagrammatic illustration in axial section of an
embodiment of a jet engine silencer, in which a silencing effect is
obtained by injecting fresh air from an air pocket situated inside
the central body through orifices formed in the wall thereof, into
the gas jet exhausting from the nozzle, said central body being
equipped with adjustable obturating flaps;
FIG. 2 is a schematic view in perspective of the central body
forming part of the silencer shown in FIG. 1;
FIG. 3 is a detail view illustrating an alternative embodiment in
which the silencer is equipped with an air ejector for improving
the supply of the inside of the central body with air drawn in from
outside the jet engine;
FIG. 4 diagrammatically illustrates a further alternative
embodiment in which the inside of the central body is supplied with
air tapped from the by-pass flow of a dualflow jet engine;
FIG. 5 diagrammatically illustrates yet another alternative
embodiment in which the inside of the central body is supplied with
air tapped from between two engine compressor stages;
FIG. 6 diagrammatically illustrates still another alternative
embodiment in which two obturating flaps cooperate with the same
orifice in the central body wall, said flaps being shown in their
operative or silencing position;
FIG. 7 is a view corresponding to FIG. 6 but in which said flaps
are shown in their inoperative position;
FIG. 8 diagrammatically illustrates a further alternative
embodiment in which the obturating flaps assume the form of hollow
bodies, said flaps being shown in their operative or silencing
position;
FIG. 9 diagrammatically illustrates yet another alternative
embodiment in which a dihedron-shaped deflecting member projects,
in its operative position, through an orifice in the central
body;
FIG. 10 is a view corresponding to FIG. 9, further depicting flaps
for masking said orifice when the dihedron-shaped deflecting member
is retracted into its inoperative position;
FIG. 11 diagrammatically illustrates another arrangement of the
invention in which an auxiliary fairing surrounds, in its operative
or silencing position, the central body in the region of the
orifice formed therein; and
FIG. 12 is a view corresponding to FIG. 11 but in which said
auxiliary fairing is in its inoperative position.
In all the figures in the drawing, like parts are designated by
like reference numerals.
Reference is first had to FIGS. 1 and 2, in which reference numeral
1 designates a jet propulsion engine terminating downstream in a
thrust nozzle 2, of axis X'-X, from which exhausts in operation a
gas jet F.
The gas jet F flows through a passage 3 bounded by the nozzle 2,
which nozzle terminates downstream in a discharge edge 2a. A
central body 5 coaxial with said nozzle extends rearwardly beyond
the discharge edge 2a thereof. Central body 5 is supported by a
cowling 4 through the agency of hollow streamlined struts 6
extending across the flow passage 3.
The central body 5 has a wall 7 longitudinally bounding a pocket 8
in the inside of said central body, which pocket is connected
through the hollow struts 6 with the surrounding atmosphere,
whereby said pocket 8 can be supplied with air drawn in from
outside the jet engine, as shown by the arrow f.
Means are provided for placing the gas jet F in contact with air
issuing from the inside of central body 5. These means include at
least one but preferably several orifices 9 formed in the
longitudinal wall 7 of the central body and through which air from
the air pocket 8 can be injected into the gas jet F as shown by the
arrow .phi..
Adjustable obturating flaps cooperate with the orifices 9 and
include, in respect of each orifice 9, a flap 10 hingedly connected
to the central body 5 and angularly adjustable in relation thereto.
In the example illustrated, each flap 10 is hingedly connected to
central body 5 about a hinge-pin 11 extending transversely in
relation to the nozzle axis. Each flap 10 includes a wall element
10a adapted to mask the associated orifice 9 whereby to restore a
substantially unbroken surface to central body wall 7, and two side
walls 10b, 10c, substantially parallel to nozzle axis X'-X and
interconnected, inter alia, by a stud 12.
Actuating means allow of pivoting the flaps 10 about the hinge-pins
11 between an operative position (shown in FIGS. 1 and 2) wherein
the orifices 9 are unmasked, and an inoperative position wherein
the same are masked. In the embodiment shown in FIGS. 1 and 2, the
actuating means include, in respect of each flap 10, a link 13
having one of its ends hingedly connected to stud 12 and its other
end fast with the rod 14a of a fluid-operated actuator 14 common to
all the flaps 10 and housed inside central body 5.
In operation, when the flaps 10 are in their operative positions
shown in FIGS. 1 and 2, they unmask the orifices 9 and at the same
time project into the gas jet F whereby to cause the internal
cross-sectional profile thereof to assume a corrugated outline
having a great perimeter.
At the location of each corrugation in said outline, an air jet
.phi. is thus injected into said jet through the associated orifice
9. The gas/air mixing surface is thereby greatly increased, which
helps to reduce the noise produced by the gas jet.
When the silencing effect is no longer required, the actuator 4 is
operated in the direction causing the flaps 10 to assume their
inoperative position (not shown) in which they mask the orifices 9
and restore a substantially unbroken surface to central body wall
7. The internal cross-sectional outline of the gas jet F then
resumes its normal non-corrugated shape and the injection of air
through the orifices 9 is stopped.
FIG. 3 relates to an alternative embodiment with respect to FIGS. 1
and 2, in which, in order to increase the rate at which air is
sucked in from outside the nozzle, there is disposed within the
hollow strut 6 or within central body 5 a jet pump or ejector 30
supplied with pressurized inducing fluid through a conduit 31. Such
ejector is preferably of the divergent fluid-wall type described in
the applicant's U.S. Pat. No. 3,216,653. In cases where nozzle 2
forms part of a turbojet engine, the said pressurized fluid may
advantageously be pressurized air tapped from a compressor of such
turbojet.
FIG. 4 depicts an alternative embodiment with respect to those
illustrated in FIGS. 1 to 3, applicable in cases where jet engine 1
is of the dual-flow or by-pass type and produces a high-pressure
and heated gas flow F.sub.1 and a low-pressure unheated air flow
F.sub.2 which is lightly compressed by an upstream fan 40. In such
cases, the air pocket 8 can be supplied with air through one or
more conduits 41 each of which is formed with an inlet orifice 41a,
disposed in such manner as to tap fresh air from the low-pressure
unheated air flow F.sub.2, and an outlet orifice 41b opening into
said air-pocket.
FIG. 5 illustrates another alternative embodiment in which the
air-pocket 8 is supplied with air through a passageway 50
originating between two stages of a multi-stage compressor and
opening into said air-pocket. In the illustrated example, the
compressor is of the dual-spool type with a low-pressure spool 51
and a high-pressure spool 52, and the passageway 50 originates
between the two compressor spools.
FIGS. 6 and 7 illustrate yet another alternative embodiment with
respect to the one depicted in FIGS. 1 and 2, wherein the
obturating flaps include, in respect of each orifice 9, a pair of
flaps 60 and 61 disposed one after the other longitudinally along
the nozzle and hinged to the central body, by their upstream and
downstream edges respectively, about hinge-pins 62 and 63 extending
transversely of the nozzle.
Each flap 60 (or 61) includes a longitudinal wall element 60a (or
61a) adapted to mask part of the associated orifice 9 and to
thereby restore a substantially unbroken surface to the wall 7 of
the central body.
Each flap 60 additionally includes two side walls 60b and 60c
substantially parallel to the nozzle axis X'-X, and each flap 61 is
movable between two fixed side walls 64b and 64c supported by the
central body and extending substantially parallel to said axis.
Each flap 60 of a pair of flaps 60, 61 is fast with an actuating
arm 65 connected through a link 66 to a similar actuating arm 67
fast with the companion flap 61, whereby upon one of said flaps
(for example flap 60) pivoting towards the nozzle axis the other
flap simultaneously pivots away therefrom. Each of actuating arms
67 is hingedly connected to the end of the rod 68a of an actuator
68 common to all the pairs of flaps 60-61 and housed inside central
body 5.
In operation, when flaps 60 and 61 are in their operative position
shown in FIG. 6, they unmask the orifices 9, whereby air jets .phi.
are injected into the gas jet F to produce a silencing effect. When
the silencing effect is no longer needed, actuator 68 is activated
to move the flaps 60 and 61 into their inoperative position (shown
for example in FIG. 7), thereby masking the orifices 9 and
restoring a substantially unbroken surface to the wall 7 of the
central body. The injection of fresh air through orifices 9 is then
stopped.
FIG. 8 shows yet another alternative embodiment in which each
orifice 9 formed in the wall 7 of central body 5 cooperates with a
flap 80 hingedly connected to the central body about a hinge-pin 81
extending transversely of the nozzle axis.
Each flap 80 is in the shape of a hollow body having three closed
faces 80a, 80b and 80c, an open upstream end 80d and a likewise
open downstream end 80e. The upstream end 80d always lies inside
the air-pocket 8 irrespective of the position of flap 80.
In operation, when flap 80 is in its operative position (shown in
FIG. 8) the orifice 9 is unmasked and the downstream end 80e of the
flap projects into the gas jet F. Two jets of fresh air from
air-pocket 8--to wit, a first jet .phi..sub.1 flowing through the
flap 80 via its open ends 80d and 80e, and a second jet .phi..sub.2
passing directly through orifice 9--are accordingly injected into
the gas jet F to produce a silencing effect. When this effect is no
longer required, flap 80 pivots about its hinge-pin 81 until its
face 80a masks orifice 9 and restores a substantially unbroken
surface to the wall 7 of the central body.
FIG. 9 illustrates an alternative possible embodiment of the
invention. Depicted in the figure is the central body 5 formed with
an orifice 9 downstream of the discharge edge 2a of nozzle 2.
Reference numeral 90 designates a deflecting member supported on
central body 5 and shaped as a dihedron having an edge 90a.
Responsively to an actuating member 91, deflecting member 90 can
occupy a deployed operative position (shown in FIG. 9) in which it
projects into the gas jet F through orifice 9, downstream of the
discharge edge 2a of nozzle 2. The dihedron edge 90a then extends
in a direction having a component transverse to the nozzle axis,
the interior of the dihedron then facing the downstream end of the
jet engine. In this position the gas jet efflux F is divided by
dihedron 90 into two partial jets which mix, on the one hand, with
the air jet .phi. passing through orifice 9 and, on the other, with
a stream of air from the surrounding atmosphere that penetrates
into the dihedron.
This enhances the silencing effect. When the latter is no longer
required, deflecting member 90 moves into a retracted inoperative
position responsively to actuating member 91, in which position it
is retracted into the cental body 5.
As shown in FIg. 10, adjustable obturating means cooperating with
the orifice 9 are likewise provided in this particular case. In the
illustrated example, such obturating means include a pair of flaps
100, 101 hingedly connected to central body 5 about hinge-pins 102,
103 respectively, each extending in a direction having a component
parallel to the nozzle axis. These flaps may occupy either an
operative position (shown in FIG. 10) in which the orifice 9 is
unmasked, or an inoperative position (not shown) in which said
orifice is masked after the deflecting member 90 has retracted into
the central body.
FIGS. 11 and 12 show an alternative arrangement of the invention.
Shown on these figures is the central body 5 formed with an orifice
9 at least part of which lies downstream of the discharge edge 2a
of nozzle 2. An auxiliary fairing, the upstream edge 110a of which
has a diameter in excess of the greatest dimension of the
downstream portion of the engine cowling 4, is disposed coaxially
with the engine.
Actuating means 111 allow of sliding the auxiliary fairing 110
parallel to the nozzle axis whereby to cause it to occupy either an
extended position (shown in FIG. 11) in which it is positioned to
form an exhaust diffuser around the gas jet F, or an inoperative
position (shown in FIG. 12) in which it surrounds the cowling
4.
In its extended position, auxiliary fairing 110 surrounds central
body 5 in the region of the orfices 9 (which are then unmasked) and
by an ejector effect allows of inducing a stream of outside air A
into the gas jet F exhausting through the nozzle 2. This enhances
the silencing effect already obtained by injecting streams of air
.phi. through the orifices 9. When this silencing effect is no
longer needed, the flaps 10 mask the orifices 9 and auxiliary
fairing 110 is moved forward once more into its inoperative
position shown in FIG. 12.
It goes without saying that changes and substitutions of parts may
be made in the non-limitative exemplary embodiments hereinbefore
described without departing from the scope of the invention as set
forth in the appended claims.
* * * * *